EP0032812B1 - Nickel base alloy and turbine engine blade cast therefrom - Google Patents

Nickel base alloy and turbine engine blade cast therefrom Download PDF

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Publication number
EP0032812B1
EP0032812B1 EP81300158A EP81300158A EP0032812B1 EP 0032812 B1 EP0032812 B1 EP 0032812B1 EP 81300158 A EP81300158 A EP 81300158A EP 81300158 A EP81300158 A EP 81300158A EP 0032812 B1 EP0032812 B1 EP 0032812B1
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EP
European Patent Office
Prior art keywords
alloy
grain boundary
stress
under
turbine engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP81300158A
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German (de)
English (en)
French (fr)
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EP0032812A1 (en
Inventor
Kenneth Harris
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Cannon Muskegon Corp
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Cannon Muskegon Corp
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Filing date
Publication date
Application filed by Cannon Muskegon Corp filed Critical Cannon Muskegon Corp
Publication of EP0032812A1 publication Critical patent/EP0032812A1/en
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Publication of EP0032812B1 publication Critical patent/EP0032812B1/en
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    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B21/00—Unidirectional solidification of eutectic materials
    • C30B21/02—Unidirectional solidification of eutectic materials by normal casting or gradient freezing
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%

Definitions

  • This invention is in the field of nickel-base casting alloys particularly intended for vacuum casting, by directional solidification, of thin wall products of complex shape for use under extremely demanding service conditions.
  • alloys in accordance with this invention suitable to use in the casting of turbine blades (including vanes) for jet engines where the castings will be subjected to extended periods of operation under very high temperatures.
  • turbine blades including vanes
  • the gas turbine industry developed the technique of directional solidification (referred to as DS) with significant improvement in high temperature alloy properties and blade performance.
  • parts cast by this technique are susceptible to grain boundary cracking.
  • nickel base alloy for vacuum directional solidification casting of thin wall, complex cored, high core-to-metal volume ratio castings for use under high stress, high temperature conditions, characterized by the absence of grain boundary cracking, consisting of the following elements in percentages by weight (other than those expressed as ppm):
  • the problem of grain boundary cracking has been particularly evident in the thin wall, first stage turbine blade and vane designs for advanced turbine engines.
  • the blades have a wall thickness of 0.635-0.762 mm (0.025-0.030 inches) with very complex coring and a high core-to-metal volume ratio.
  • This type of casting requires a very high strength alloy.
  • This type of casting has been impractical to manufacture from some existing alloys with the required high temperature strength because of potential failure resulting from grain boundary cracking, occurring during the DS casting of the parts. This is a very serious problem in high performance turbine blades and vanes.
  • the operation conditions are such that structural failure is intolerable. Thus, complete and thorough inspection of each part is required.
  • the alloy remain metallurgically stable under the severe temperature of its operating environment.
  • the M is mainly W and Mo. While the presence of W and Mo increases the tendency to formation of the acicular M a C phase, these elements along with Ta cannot be eliminated because of their essential role in strengthening at high temperatures.
  • the low value for N v3B is indicative that no deleterious sigma phase formation will occur.
  • the reduction in C is important in accomplishing the minimized M a C acicular phase formation by reducing the initial as-cast formation of interdendritic and grain boundary MC (Hf, Ta, Ti) carbides.
  • interdendritic and grain boundary MC Hf, Ta, Ti
  • the fact that the amount of C could be reduced while improving alloy characteristics is significant because C, while essential to the formation of interdendritic and grain boundary carbides, is essential to the strength and stability of the alloy.
  • Zr a known source of increased alloy creep strength, was also a causative of grain boundary crack sensitivity, although the reason for this is not fully understood. It is known that Zr migrates to the grain boundaries in these cast Nickel-base alloys.
  • Alloys in accordance with this invention not only exhibit virtual or total elimination of the grain boundary cracking problem without unacceptable sacrifice of high temperature strength, but also have dependable repeatability under commercially acceptable manufacturing and foundry use conditions.
  • This equipment includes an outer mould shell 10 and an inner tubular mould shell 11 of alumina.
  • the shells were spaced apart at top and bottom and held in concentric relationship by spacer rings 12. Communication is provided between the interior of the inner shell and the annular space between the shells by a pair of vertical channels 13 at the bottom of the inner shell.
  • the radial spacing between the shells 10 and 11 forming the annular channel 14 was 0.15 mm and the outside diameter of the shell 11 was 1.9 mm.
  • the test unit was placed on a chill plate 15. The unit was surrounded by an induction heater 16. A rod of the alloy from heat VF-165 was placed within the inner shell 11. The induction heater was turned on to melt the alloy causing it to flow through the channels 13 into the annular space 14.
  • blades C Approximately 20 directionally solidified, complex cored, thin wall blades (hereinafter referred to as blades C) were vacuum cast from the alloy of the same heat (VF-165) as that tested in Example I. These were cast using a European-developed, directional solidification, casting process. Identical blades (hereinafter referred to as blades D) were cast from heats V-5134 and V-5224 of the alloy set out in Column B of Table I, except for the following differences:
  • the blades also were cut up and microscopically inspected for microporosity.
  • the blades were found to have internal microporosity of ⁇ 0.2% with most of the fields exhibiting a microporosity of about 0.1 %.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP81300158A 1980-01-17 1981-01-14 Nickel base alloy and turbine engine blade cast therefrom Expired EP0032812B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11303780A 1980-01-17 1980-01-17
US113037 1980-01-17

Publications (2)

Publication Number Publication Date
EP0032812A1 EP0032812A1 (en) 1981-07-29
EP0032812B1 true EP0032812B1 (en) 1984-03-14

Family

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Family Applications (1)

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EP81300158A Expired EP0032812B1 (en) 1980-01-17 1981-01-14 Nickel base alloy and turbine engine blade cast therefrom

Country Status (3)

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EP (1) EP0032812B1 (enExample)
JP (1) JPS56108852A (enExample)
DE (1) DE3162552D1 (enExample)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU630623B2 (en) * 1988-10-03 1992-11-05 General Electric Company An improved article and alloy therefor
US5173255A (en) * 1988-10-03 1992-12-22 General Electric Company Cast columnar grain hollow nickel base alloy articles and alloy and heat treatment for making
US5069873A (en) * 1989-08-14 1991-12-03 Cannon-Muskegon Corporation Low carbon directional solidification alloy
WO1993024683A1 (en) * 1992-05-28 1993-12-09 United Technologies Corporation Oxidation resistant single crystal superalloy castings
CN1053708C (zh) * 1995-01-26 2000-06-21 中国科学院金属研究所 一种定向凝固优质铸造镍基高温合金
US9322089B2 (en) * 2006-06-02 2016-04-26 Alstom Technology Ltd Nickel-base alloy for gas turbine applications
GB2513852B (en) * 2013-05-03 2015-04-01 Goodwin Plc Alloy composition

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3677747A (en) * 1971-06-28 1972-07-18 Martin Marietta Corp High temperature castable alloys and castings
FR2118621A5 (enExample) * 1970-12-14 1972-07-28 Martin Metals Co
FR2216361A1 (enExample) * 1973-02-06 1974-08-30 Cabot Corp
FR2374427A1 (fr) * 1976-12-16 1978-07-13 Gen Electric Alliage a base de nickel perfectionne et piece coulee obtenue a partir de cet alliage

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3526499A (en) * 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2118621A5 (enExample) * 1970-12-14 1972-07-28 Martin Metals Co
US3677747A (en) * 1971-06-28 1972-07-18 Martin Marietta Corp High temperature castable alloys and castings
FR2216361A1 (enExample) * 1973-02-06 1974-08-30 Cabot Corp
FR2374427A1 (fr) * 1976-12-16 1978-07-13 Gen Electric Alliage a base de nickel perfectionne et piece coulee obtenue a partir de cet alliage

Also Published As

Publication number Publication date
DE3162552D1 (en) 1984-04-19
EP0032812A1 (en) 1981-07-29
JPS56108852A (en) 1981-08-28
JPS6146539B2 (enExample) 1986-10-15

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